@A330

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 53

TITLE: FUSELAGE - CENTER FUSELAGE - CIRCUMFERENTIAL JOINT FRAME

53.3, STGR 13 LH TO STGR 13 RH - FATIGUE LIFE IMPROVEMENT

MODIFICATION No.: 49403S16334

This page transmits Revision No.02 of Service Bulletin No.A330-53-3127

ADDITIONAL WORK

**CONF ALL

NOTE: No additional work is required by this revision for aircraft modified by any previous

issue.

REASON

Revision No. 02 is issued to add the new thresholds and modify the Appendix 01.

CHANGES

SUMMARY

MODIFICATIONS Minor editorial or document structure change N

REASON/DESCRIPTION/OPERATIONAL

CONSEQUENCES

Minor editorial or document structure change N

GENERAL EVALUATION Minor editorial or document structure change N

MATERIAL PRICE INFORMATION Minor editorial or document structure change N

EFFECTIVITY Minor editorial or document structure change N

CONCURRENT REQUIREMENTS Minor editorial or document structure change N

REFERENCES / REPERCUSSIONS Minor editorial or document structure change N

NATURE OF THE WORK Minor editorial or document structure change N

MANPOWER Minor editorial or document structure change N

APPENDICES Minor editorial or document structure change N

Fig. A-FSAAA Minor editorial or document structure change N

Fig. A-FSAAA Sheet 01 Minor editorial or document structure change N

PLANNING INFORMATION

EFFECTIVITY Minor editorial or document structure change N

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Configuration definition Minor editorial or document structure change N

CONF 001 Minor editorial or document structure change N

Material Effectivity Minor editorial or document structure change N

Minor editorial or document structure change N

CONCURRENT REQUIREMENTS Minor editorial or document structure change N

REASON Minor editorial or document structure change N

History Minor editorial or document structure change N

Objective/Action Minor editorial or document structure change N

Advantages Minor editorial or document structure change N

Operational/Maintenance

Consequences

Minor editorial or document structure change N

DESCRIPTION Minor editorial or document structure change N

COMPLIANCE Minor editorial or document structure change N

Classification Minor editorial or document structure change N

Accomplishment Timescale Threshold revised N

APPROVAL Minor editorial or document structure change N

Minor editorial or document structure change N

MANPOWER Minor editorial or document structure change N

Minor editorial or document structure change N

WEIGHT AND BALANCE Minor editorial or document structure change N

Minor editorial or document structure change N

ELECTRICAL LOAD DATA Minor editorial or document structure change N

REFERENCES Minor editorial or document structure change N

Minor editorial or document structure change N

PUBLICATION AFFECTED Minor editorial or document structure change N

Minor editorial or document structure change N

INTERCHANGEABILITY/MIXABILITY Minor editorial or document structure change N

SPARES Minor editorial or document structure change N

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY Minor editorial or document structure change N

Procurement Addresses Minor editorial or document structure change N

Price and Availability Minor editorial or document structure change N

INDUSTRY SUPPORT INFORMATION Minor editorial or document structure change N

LIST OF COMPONENTS Minor editorial or document structure change N

Kit 533127A01R05 Minor editorial or document structure change N

LIST OF MATERIALS - OPERATOR

SUPPLIED

Minor editorial or document structure change N

Consumable Materials Minor editorial or document structure change N

Consumable CMLA01 Minor editorial or document structure change N

Components Minor editorial or document structure change N

Equipment Minor editorial or document structure change N

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

PARTS TO BE RE-IDENTIFIED BY

OPERATOR

Minor editorial or document structure change N

TOOLING Minor editorial or document structure change N

Tooling - Price and Availability Minor editorial or document structure change N

Tools Minor editorial or document structure change N

Special Tools Minor editorial or document structure change N

ACCOMPLISHMENT INSTRUCTIONS

TASK 533127- 831-801-001-

MODIFICATION

Minor editorial or document structure change N

Task associated data - 001 Minor editorial or document structure change N

Subtask 533127-910-001-001 Minor editorial or document structure change N

Subtask 533127-839-001-001 Minor editorial or document structure change N

Subtask 533127-941-001-001 Minor editorial or document structure change N

Subtask 533127-831-004-001 Minor editorial or document structure change N

Subtask 533127-831-005-001 Minor editorial or document structure change N

Subtask 533127-831-006-001 Minor editorial or document structure change N

Subtask 533127-831-007-001 Minor editorial or document structure change N

Subtask 533127-831-008-001 Minor editorial or document structure change N

Subtask 533127-700-009-001 Minor editorial or document structure change N

Subtask 533127-942-010-001 Minor editorial or document structure change N

Fig. A-FBAAA Minor editorial or document structure change N

Fig. A-FBAAA Sheet 01 Minor editorial or document structure change N

Fig. A-FBAAA Sheet 02 Minor editorial or document structure change N

Fig. A-FBAAA Sheet 03 Minor editorial or document structure change N

Fig. A-FBAAA Sheet 04 Minor editorial or document structure change N

Fig. A-FBAAA Sheet 05 Minor editorial or document structure change N

Fig. A-FBAAA Sheet 06 Minor editorial or document structure change N

Fig. A-FBAAA Sheet 07 Minor editorial or document structure change N

Fig. A-FBAAA Sheet 08 Minor editorial or document structure change N

Appendix - 01

APPENDIX CONTENT Minor editorial or document structure change N

Fig. A-FAAAA Minor editorial or document structure change N

Fig. A-FAAAA Sheet 01 Minor editorial or document structure change N

Fig. A-FABAA Minor editorial or document structure change N

Fig. A-FABAA Sheet 01 Minor editorial or document structure change N

Fig. A-FACAA Minor editorial or document structure change N

Fig. A-FACAA Sheet 01 Minor editorial or document structure change N

Appendix - 02

APPENDIX CONTENT Minor editorial or document structure change N

Fig. A-FADAA Minor editorial or document structure change N

Fig. A-FADAA Sheet 01 Minor editorial or document structure change N

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

FILLING INSTRUCTIONS

This Service Bulletin has been generated electronically and is reissued as a complete document.

Replace the complete document.

Put this Revision Transmittal Sheet in front of the Service Bulletin.

HISTORY OF PREVIOUS REVISIONS

No previous revisions.

Revision No. 01 issued to supersede Airworthiness Directive (Consigne de Navigabilite) No.

2002-529(B) by No. F-2003-415(B), to modify the manpower and Kit 533127A01R05 further to

validation of this Service Bulletin on MSN 0059.

Also, Mat. No. 09-013 has been added.

REVISION SEQUENCE

ORIGINAL: Oct 30/02

REVISION No. : 02 - Dec 07/11

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SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

This summary is for information only and is not approved for modification of the aircraft.

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 53

TITLE: FUSELAGE - CENTER FUSELAGE - CIRCUMFERENTIAL JOINT FRAME

53.3, STGR 13 LH TO STGR 13 RH - FATIGUE LIFE IMPROVEMENT

**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATION

MAJOR 49403S16334

MINOR None

NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the

mass, balance, structural strength, reliability, operational characteristics affecting the

airworthiness of the product. All other changes are major changes.

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

Further to damages occurred during fatigue tests, it has been decided to install an external stiffener of

butt strap type at the upper part of the circumferential joint at Frame 53.3, in order to improve fatigue

life.

This Service Bulletin requires the reinforcement of the circumferencial joint at the upper part at Frame

53.3 by installing external stiffeners between LH and RH STGR13.

Accomplishment of this Service Bulletin will allow improving fatigue life of the circumferencial joint at

Frame 53.3 and will thus postpone the next inspection to beyond the design service goal.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN YES VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

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SERVICE BULLETIN

SUMMARY

MATERIAL PRICE INFORMATION

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 533127A01R05 1 13,390.00 Butt Straps, Shims

EFFECTIVITY

This Service Bulletin is applicable to this (these) operator(s) :

BEL CPA G8E HDA HFY MAS OHY THA TSC VLK XAX

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

Task 533127-831-801-001: MODIFICATION

TOTAL MANHOURS 314.50

ELAPSED TIME (HOURS) 56.25

APPENDICES

Appendix - 01

Appendix - 02

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SERVICE BULLETIN

SUMMARY

**CONF ALL

FR38

FR54

STGR5

STGR5

STGR13

FR53.3

BUTT STRAPS

G_SB_533127_5_SAAA_01_00

Figure A-FSAAA - Sheet 01

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

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SERVICE BULLETIN

SUMMARY

This Page Intentionally Left Blank

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

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@A330

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 53

TITLE: FUSELAGE - CENTER FUSELAGE - CIRCUMFERENTIAL JOINT FRAME

53.3, STGR 13 LH TO STGR 13 RH - FATIGUE LIFE IMPROVEMENT

MODIFICATION No.: 49403S16334

This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the

property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with

any information contained in it. It is delivered on the express condition that said document and the

information contained in it shall be treated as confidential, shall not be used for any purpose other than

that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall

not be duplicated in any manner (except for the purposes of performing the tasks described hereunder

and provided that any recipient of such document shall comply with the conditions herein), without

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

NOTE: This modification is only applicable to aircraft on which

Mod. No. 41652S11819 (FUSELAGE-STRUCTURE-INTRODUCE A340

COMMONALITY ITEMS) is not embodied.

This Service Bulletin has been validated on A330 aircraft 0059.

(1) Models

330-301 330-321 330-322 330-342

(2) Effectivity by MSN

0012 0017 0030 0037 0045 0050 0054-0055 0059-0060 0062 0064-0067 0069-0073

0077 0082-0083 0086-0087 0095-0096 0098-0100 0102 0106-0107 0109-0112

(3) Effectivity by Operator

The Operator/MSN relationship is provided for information only and is correct at the time

of issue in accordance with the information available to AIRBUS. Any future changes

resulting from transfer of an aircraft from one operator to another will not be reflected in

this list unless the Service Bulletin is revised for another reason.

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@A330

SERVICE BULLETIN

OPERATOR MSN

BEL 0030 0037 0045 0082 0095

CPA 0012 0017 0071 0102

G8E 0059

HDA 0083 0099 0106 0109

HFY 0096

MAS 0067 0069 0073 0077 0100 0107 0110

OHY 0072 0087 0098

THA 0050 0060 0062 0064 0065 0066 0112

TSC 0111

VLK 0055 0070 0086

XAX 0054

(4) Configuration by MSN

MSN CONFIGURATION

0012 0017 0030 0037 0045 0050 0054 0055 0059 0060 0062

0064 0065 0066 0067 0069 0070 0071 0072 0073 0077 0082

0083 0086 0087 0095 0096 0098 0099 0100 0102 0106 0107

0109 0110 0111 0112

001

(5) Configuration definition

**CONF 001

Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a

standard configuration.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Kit 533127A01R05 1

Consumable CMLA01 1

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

Further to damages occurred during fatigue tests, it has been decided to install an

external stiffener of butt strap type at the upper part of the circumferential joint at Frame

53.3, in order to improve fatigue life.

(2) Objective/Action

This Service Bulletin requires the reinforcement of the circumferencial joint at the upper

part at Frame 53.3 by installing external stiffeners between LH and RH STGR13.

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

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SERVICE BULLETIN

(3) Advantages

Accomplishment of this Service Bulletin will allow improving fatigue life of the

circumferencial joint at Frame 53.3 and will thus postpone the next inspection to beyond

the design service goal.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 533127-831-801-001: MODIFICATION

(1) Install the butt strap Item 6 and the shims Item 12 at FR53.3, on the fuselage skin

between LH and RH STGR5.

(2) Install the butt strap Item 7 and the shim Item 9 at FR53.3, on the fuselage skin

between LH STGR5 and LH STGR13

(3) Install the butt strap Item 8 and the shim Item 10 at FR53.3, on the fuselage skin

between RH STGR5 and RH STGR13

(4) Apply sealant around the butt straps

(5) Paint the modified area

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

Compliance Times

(Whichever occurs first)

Condition Action

Threshold Grace Period

Interval

For the Short

Range (SR)

Mission : 15,300FC

/ 46,100FH

Config. 001 Do the TASK None

533127-831-801

001

MODIFICATION

For the Long

Range (LR)

Mission : 13,200FC

/ 79,300FH

None

None

Accomplishment Timescale Table

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SERVICE BULLETIN

One set of threshold (Short Range, Threshold (SR) and Long Range, Threshold (LR))

has been established. This set ensure continued airworthiness and could be used to

cover any type of A/C utilization. This approach is an equivalent damage approach

corresponding to a trade off between FC/FH to better suit the fleet utilization. As the set

of thresholds ensure continued airworthiness and could be used to cover any type of

utilization, for the 1st inspection, operators may select either SR (Threshold) or LR

(Threshold) (depending of the A/C utilization evolution). If a non optimal set of threshold

is selected, airworthiness will be ensured, but will penalize the operator because the

inspection will be performed sooner than necessary. As a consequence, the selection of

SR or LR threshold can be changed whenever. Threshold is whichever occurs first

between FC and FH for a set of threshold between SR and LR. This means that the set

FC/FH must be considered jointly (ie FCSR cannot be used with FHLR and vice versa).

This Service Bulletin has been classified Mandatory by the issue of an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must

be used as the reference document for the mandated accomplishment timescale.

F. APPROVAL

The technical content of this document is approved under the authority of Design

Organisation Approval No. EASA.21J.031.

If an aircraft listed in the effectivity has a modification or repair embodied that is not of

AIRBUS origin, and which affects the content of this Service Bulletin, the operator is

responsible for obtaining approval by its airworthiness authority for any adaptation necessary

before incorporation of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are based on the direct labor cost to

do the work. These estimates assume that the work will be done by experienced personnel,

and may need to be revised upwards to suit operator’s circumstances. The estimates do not

include the time to prepare, plan or inspect the work. Manufacture and procurement of parts

and tools, drying times for paints, sealants, etc., and general administration work are also not

included.

Task 533127-831-801-001: MODIFICATION

Get Access 66.00

On Aircraft

Install the butt strap Item 6 and the shims Item 12 at

FR53.3, on the fuselage skin between LH and RH

STGR5.

57.00

Install the butt strap Item 7 and the shim Item 9 at

FR53.3, on the fuselage skin between LH STGR5 and

LH STGR13

57.00

Install the butt strap Item 8 and the shim Item 10 at

FR53.3, on the fuselage skin between RH STGR5 and

RH STGR13

57.00

Apply sealant around the butt straps 4.00

Paint the modified area 4.50

Tests 3.00

Close-Up 66.00

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

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SERVICE BULLETIN

Task 533127-831-801-001: MODIFICATION

TOTAL MANHOURS 314.50

ELAPSED TIME (HOURS) 56.25

NOTE: For the elapsed time assumptions, refer to Appendix - 02 .

H. WEIGHT AND BALANCE

The weight and balance estimates given in this Service Bulletin are based on the

Manufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition of

MEW and operator’s items refer to Weight and Balance Manual (WBM) Chapter 1-00-07.

Manufacturers Empty Weight +4.3 KG (+9.4797 LB)

Effect on Balance +173.982 KGM (+1258.411 LB.FT )

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) 05-53-00 12-34-24 20-21-11

21-20-00 25-23-41 25-24-51

25-24-61 25-80-00 52-10-00

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-55-00

Non Destructive Test Manual (NTM) 51-10-01

Standards Manual (SM)

Structural Repair Manual (SRM) 51-21-11 51-23-11 51-42-11

51-43-00 51-46-11 51-48-00

51-76-11

Weight and Balance Manual (WBM) Chapter 1-00-07

Aircraft Maintenance Manual (AMM) 07-11-00

Structural Repair Manual (SRM) 51-51-00

K. PUBLICATION AFFECTED

Structural Repair Manual (SRM) 53-31-11

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

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SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Customers with aircraft shown in the effectivity of this Service Bulletin should send a

purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is :

Kit 533127A01R05 AIRBUS Material, Logistics and Suppliers

Weg beim Jaeger 150

D-22335 HAMBURG

GERMANY

For ordering by internet:

http://spares.airbus.com

For ordering by fax: +49 40 50 76 2590

For ordering by E-mail: airbus.kit@airbus.com

(2) Price and Availability

Kit 533127A01R05

Cost 13,390.00 USD

Availability 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements. The sales terms (costs

and availability) are estimated in relation to economic conditions at the issue date of the

Service Bulletin.

B. INDUSTRY SUPPORT INFORMATION

This Service bulletin is subject to the Fatigue Test Integration Program. Refer to the FTIP

policy.

C. LIST OF COMPONENTS

Kit 533127A01R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

1 ASNA2528-4 744 Nut

2 ASNA2026V4-8 284 Bolt

3 ASNA2026V4-11 432 Bolt

5 ASNA2026V4-13 88 Bolt

6 F5332579020096 1 Strap

7 F5332579120096 1 Strap

8 F5332579120196 1 Strap

9 F5332579220096 1 Shim

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

10 F5332579220196 1 Shim

11 ASNA2531-4 60 Nut

12 F5332578120095 2 Shim

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013 As required

Sealant 09-016 As required

Solvent General Purpose 11-026 As required

Chemical Conversion Coating 13-002 As required

Anti-Corrosion Primer 16-001 As required

Polyurethane Top Coat Grey 16-002 As required

External Decoration Paint 16-016 As required

External Top Coat 16-018 As required

Wash Primer 16-020 As required

(2) Components

None

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

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SERVICE BULLETIN

(2) Tools

- Fatigue Technology Incorporated (FTI) has allocated tool kit number FTIA330-53-3127-1 for accomplishment of this Service Bulletin. Operators interested in

obtaining the FTI tool kit should contact :

Fatigue Technology Inc.

401 Andover Park East

SEATTLE WA 98188-7605

USA

Tel : (206) 246-2010

Telex : 321004

Fax : (206) 244-9886

To accomplish this Service Bulletin, it is necessary to use the following tools and

equipment :

- Equipment and materials for check of holes as per NTM 51-10-01, Part 6,

Procedure A.

- Equipment and materials for the jacking procedure (Refer to Appendix - 01 ).

(3) Special Tools

None

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 533127-831-801-001 - MODIFICATION

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS :

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC., AS

NECESSARY ON WIRING AND COMPONENTS

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.

Task Associated Data

Zone

250

Manpower

TOTAL MANHOURS 314.50

ELAPSED TIME (HOURS) 56.25

A. GENERAL

(1) Subtask 533127-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

Chemical Conversion

Coating

13-002 As required

Anti-Corrosion Primer 16-001 As required

Polyurethane Top Coat

Grey

16-002 As required

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

REVISION No.: 02 - Dec 07/11 Page: 11

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ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

External Decoration Paint 16-016 As required

External Top Coat 16-018 As required

Wash Primer 16-020 As required

References

Aircraft Maintenance Manual (AMM) 20-21-11, Page Block 201

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-21-11

51-23-11

51-42-11

51-43-00

51-46-11

51-48-00

51-76-11

(a) For the specification of the material numbers (Mat. No.), refer to the CML.

(b) Remove and install the fasteners, (Refer to SRM 51-42-11).

(c) For the cold expansion of the fastener holes, (Refer to SRM 51-48-00).

(d) Countersink the holes, (Refer to SRM 51-46-11).

(e) Clean the surface to seal with :

Solvent General

Purpose

11-026 As required

(f) To apply sealant, (Refer to SRM 51-76-11).

(g) Torque the standard threaded fasteners, (Refer to AMM 20-21-11 Page Block 201).

(h) For alternative and substitute fasteners (Refer to SRM 51-43-00).

(i) Renew the protective finish with :

(Refer to SRM 51-21-11 and SRM 51-23-11)

Chemical

Conversion Coating

13-002 As required

or

Wash Primer 16-020 As required

and

Anti-Corrosion

Primer

16-001 As required

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

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Polyurethane Top

Coat Grey

16-002 As required

and

External Top Coat 16-018 As required

or

External Decoration

Paint

16-016 As required

(j) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fasteners grip length in accordance with SRM Chapter 51.

(2) Subtask 533127-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in the

Service Bulletin.

B. PREPARATION

(1) Subtask 533127-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201

21-20-00, Page Block 401

25-23-41, Page Block 401

25-24-51, Page Block 401

25-24-61, Page Block 401

25-80-00, Page Block 201

52-10-00, Page Block 201

(a) Electrically ground the aircraft, (Refer to AMM 12-34-24 Page Block 201).

(b) Put the access platform(s) in position.

(c) Open the passenger/crew door 831, (Refer to AMM 52-10-00 Page Block 201).

(d) Remove the ceiling panels 251PC, 251QC, 252PC and 252QC, (Refer to AMM

25-23-41 Page Block 401).

(e) Remove the center stowage compartment at Frame 53.3, (Refer to AMM 25-24-61

Page Block 401).

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

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(f) Remove the LH and RH lateral overhead stowage compartments at Frame 53.3,

(Refer to AMM 25-24-51 Page Block 401).

(g) Remove the air distribution ducts for an easier access to the work area, (Refer to

AMM 21-20-00 Page Block 401).

(h) Disengage the electrical wires and the insulation blankets from the work area,

(Refer to AMM 25-80-00 Page Block 201).

NOTE: If necessary, disengage the support plates of the decoder/encoder

units 200RH17 and 200RH18 to get access to the work area. Hold

the support plates because you must not pull the electrical wires.

Retain the fasteners.

(i) Do the jacking procedure, (Refer to Appendix - 01 ).

C. PROCEDURE

WARNING: WEAR AND ATTACH A SAFETY HARNESS WHEN YOU WORK ON HIGH

SECTIONS. A FALL CAN KILL OR INJURE YOU.

NOTE: Do not remove all the fasteners from the fuselage at the same time. First,

remove the fasteners between the LH and RH STGR 5 and install the upper

butt strap Item 6 and the shims Item 12. Then you can remove the other

fasteners and install the butt strap Items 7 and 8, and the shims Items 9 and

10 at the same time.

(1) Subtask 533127-831-004-001 - Install the butt strap Item 6 and the shims Item 12 at

FR53.3, on the fuselage skin between LH and RH STGR5.

Work Zones and Access Panels

Zone Access/Work location

250 Work location Frame 53.3

from Stringer 5 LH to Stringer 5 RH

Manpower Resources

Manhours 57.00

Minimum number of person 4

Subtask elapsed time 14.25

Skills AIRFRAME

Material necessary to do the job

Kit 533127A01R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2528-4 264 Nut

2 ASNA2026V4-8 96 Bolt

3 ASNA2026V4-11 160 Bolt

5 ASNA2026V4-13 36 Bolt

6 F5332579020096 2 Strap

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

11 ASNA2531-4 28 Nut

12 F5332578120095 4 Shim

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013 As required

Sealant 09-016 As required

Chemical Conversion

Coating

13-002 As required

Anti-Corrosion Primer 16-001 As required

Polyurethane Top Coat

Grey

16-002 As required

References

Non Destructive Test Manual (NTM) 51-10-01 Part 6, Procedure A

Fig. A-FBAAA

Butt Strap Installation

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

(a) Remove the fasteners between LH and RH STGR5

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 02 and Fig. A-FBAAA Sheet

05

1 From the LH side, remove :

Refer to Fig. A-FBAAA Sheet 02

140 Nut Item (1) Discard

48 Bolt Item (2) Discard

78 Bolt Item (3) Discard

14 Bolt Item (5) Discard

Refer to Fig. A-FBAAA Sheet 05

6 Nut Item (1) Discard

2 Bolt Item (3) Discard

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

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SERVICE BULLETIN

4 Bolt Item (5) Discard

2 From the RH side, remove :

Refer to Fig. A-FBAAA Sheet 02

140 Nut Item (1) Discard

48 Bolt Item (2) Discard

78 Bolt Item (3) Discard

14 Bolt Item (5) Discard

Refer to Fig. A-FBAAA Sheet 05

6 Nut Item (1) Discard

2 Bolt Item (3) Discard

4 Bolt Item (5) Discard

(b) Do an inspection of the holes

1 Do a rototest in the 152 holes of the removed bolts, (Refer to NTM 51-10-01

Part 6, Procedure A), (Refer to Fig. A-FBAAA Sheet 02).

2 If a crack is found, contact AIRBUS.

3 If no crack is found, do the steps that follow.

(c) Put the butt strap and the shims in position on the skin between LH and RH

STGR5

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 06, Fig. A-FBAAA Sheet 07

and Fig. A-FBAAA Sheet 08

1 As shown in View E, Section AA and Section DD, put in position and hold :

1 Butt Strap F5332579020096 Item 6

2 Shim F5332578120095 Item 12

NOTE (1): Put the shims Item 12 in position between the fuselage skin

and the butt strap Item 6 to fill the clearance between the skin

and the butt strap.

(d) Counter-drill the fastener holes in the butt strap Item 6 and the shims Item 12

(Refer to Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 02

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

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CAUTION: DO NOT DRILL THE 12 HOLES AT LH AND RH STGR5 AT THIS

TIME. YOU WILL DRILL THESE HOLES DURING THE COLD

EXPANSION STEP.

1 In the butt strap Item 6 and in the shims Item 12 , counter-drill 280 holes,

temporarily attach the butt strap at the same time.

(e) Deburr the holes.

(f) For the cold expansion of the 12 holes at LH and RH STGR5 do the steps that

follow :

Refer to Fig. A-FBAAA Sheet 05

1 For the cold expansion, use the tools supplied in Kit FTI-A330-53-3127-1.

2 On the LH and the RH sides, counter-drill 12 holes in the butt strap Item 6 and

in the shims Item 12.

3 Ream the 12 holes to the start hole diameter between 5.75 mm and 5.79 mm

(0.22638 in. and 0.22795 in.).

4 Deburr the holes.

5 Identify with a mark the LH and RH sides on the butt strap Item 6 before

removal, to prevent a wrong position when you install it.

NOTE: If necessary, adjust the length of the butt strap Item 6 and the

shims Item 12.

Renew the protective finish on the reworked surfaces with :

Chemical

Conversion Coating

13-002 As required

Anti-Corrosion

Primer

16-001 As required

Polyurethane Top

Coat Grey

16-002 As required

6 Remove the butt strap Item 6 and the shims Item 12.

7 Do the cold expansion of the holes in the fuselage.

(g) Apply to the attachment areas between the butt strap, the shims and the fuselage :

Sealant 09-016 As required

(h) Install the butt strap Item 6 and the shims Item 12

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 02, Fig. A-FBAAA Sheet 05,

Fig. A-FBAAA Sheet 06, Fig. A-FBAAA Sheet 07 and Fig. A-FBAAA Sheet 08

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

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1 Put the butt strap and the shims in position on the skin, between LH and RH

STGR5 :

1 Butt Strap F5332579020096 Item 6

2 Shim F5332578120095 Item 12

NOTE: Temporarily attach the parts.

Smooth the burr of sealant.

Let the sealant dry as necessary.

(i) Ream the fastener holes in the butt strap and the shims

NOTE: Ream the holes from the inner side of the fuselage.

To prevent butt strap debonding during reaming, do not remove all

the temporary fasteners at the same time. Install the new fasteners

in the reamed holes one after the other as specified in the steps

that follow.

1 Ream the 12 cold expanded holes to the finish hole diameter between 6.227

mm. and 6.262 mm (0.24516 in. and 0.24654 in.).

Refer to Fig. A-FBAAA Sheet 05

2 Ream the 280 holes to a diameter between 6.310 mm and 6.350 mm

(0.24842 in. and 0.25000 in.).

Refer to Fig. A-FBAAA Sheet 02

(j) Countersink the 292 holes in the butt strap Item 6 for the bolts Items 2, 3 and 4.

(k) Deburr the holes.

(l) Attach the butt strap Item 6 and the shims Item 12 with :

Refer to Fig. A-FBAAA Sheet 02 and Fig. A-FBAAA Sheet 06

96 Bolt ASNA2026V4-8 Item 2

156 Bolt ASNA2026V4-11 Item 3

28 Bolt ASNA2026V4-13 Item 5

264 Nut ASNA2528-4 Item 1

16 Nut ASNA2531-4 Item 11

Refer to Fig. A-FBAAA Sheet 05 and Fig. A-FBAAA Sheet 06

4 Bolt ASNA2026V4-11 Item 3

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

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SERVICE BULLETIN

8 Bolt ASNA2026V4-13 Item 5

12 Nut ASNA2531-4 Item 11

NOTE: Apply to the countersunk holes before fastener installation :

Corrosion Inhibiting

Brush Consistency

09-013 As required

(2) Subtask 533127-831-005-001 - Install the butt strap Item 7 and the shim Item 9 at

FR53.3, on the fuselage skin between LH STGR5 and LH STGR13

Work Zones and Access Panels

Zone Access/Work location

250 Work location Frame 53.3

from Stringer 5 LH to Stringer 13 LH

Manpower Resources

Manhours 57.00

Minimum number of person 4

Subtask elapsed time 14.25

Skills AIRFRAME

Material necessary to do the job

Kit 533127A01R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2528-4 240 Nut

2 ASNA2026V4-8 94 Bolt

3 ASNA2026V4-11 136 Bolt

5 ASNA2026V4-13 26 Bolt

7 F5332579120096 2 Strap

9 F5332579220096 2 Shim

11 ASNA2531-4 16 Nut

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013 As required

Sealant 09-016 As required

Chemical Conversion

Coating

13-002 As required

Anti-Corrosion Primer 16-001 As required

Polyurethane Top Coat

Grey

16-002 As required

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

REVISION No.: 02 - Dec 07/11 Page: 19

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SERVICE BULLETIN

References

Non Destructive Test Manual (NTM) 51-10-01 Part 6, Procedure A

Fig. A-FBAAA

Butt Strap Installation

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

(a) Remove the fasteners between LH STGR5 and LH STGR13

Refer to Fig. A-FBAAA Sheet 03 and Fig. A-FBAAA Sheet 04

1 Between LH STGR5 and LH STGR13, remove :

Refer to Fig. A-FBAAA Sheet 03

128 Nut Item (1) Discard

56 Bolt Item (2) Discard

72 Bolt Item (3) Discard

Refer to Fig. A-FBAAA Sheet 04

128 Nut Item (1) Discard

38 Bolt Item (2) Discard

64 Bolt Item (3) Discard

26 Bolt Item (5) Discard

(b) Do an inspection of the holes

1 Do a rototest in the 128 holes of the removed bolts, (Refer to NTM 51-10-01

Part 6, Procedure A), (Refer to Fig. A-FBAAA Sheet 03 and Fig. A-FBAAA

Sheet 04).

2 If a crack is found, contact AIRBUS.

3 If no crack is found, do the steps that follow.

(c) Put the butt strap in position on the skin between LH STGR5 and LH STGR13

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 06, Fig. A-FBAAA Sheet 07

and Fig. A-FBAAA Sheet 08

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

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1 As shown in View E, Section BB, Section CC and Section DD, put in position

and hold :

1 Butt Strap F5332579120096 Item 7

1 Shim F5332579220096 Item 9

NOTE (1): Put the shim Item 9 in position between the fuselage skin and

the butt strap Item 7 to fill the clearance between the skin and

the butt strap.

(d) Counter-drill the fastener holes in the butt strap Item 7 and shim Item 9

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 03 and Fig. A-FBAAA Sheet

04

1 In the butt strap Item 7 and the shim Item 9, counter-drill 256 holes,

temporarily attach the butt strap at the same time.

(e) Deburr the holes.

(f) Identify with a mark the upper and lower sides on the butt strap Item 7 before

removal, to prevent a wrong position when you install it.

NOTE: If necessary, adjust the length of the butt strap Item 7 and the

shims Item 9.

Renew the protective finish on the reworked surfaces with :

Chemical

Conversion Coating

13-002 As required

Anti-Corrosion

Primer

16-001 As required

Polyurethane Top

Coat Grey

16-002 As required

(g) Remove the butt strap Item 7 and the shim Item 9.

(h) Apply to the attachment areas between the butt strap, the shim and the fuselage :

Sealant 09-016 As required

(i) Install the butt strap Item 7 and the shim Item 9

Refer to Fig. A-FBAAA Sheet 06, Fig. A-FBAAA Sheet 07 and Fig. A-FBAAA Sheet

08

1 Put the butt strap and the shim in position on the skin, between LH STGR5

and LH STGR13 :

1 Butt Strap F5332579120096 Item 7

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

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1 Shim F5332579220096 Item 9

NOTE: Temporarily attach the parts.

Smooth the burr of sealant.

Let the sealant dry as necessary.

(j) Ream the 256 holes to a diameter between 6.310 mm and 6.350 mm (0.24842 in.

and 0.25000 in.).

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 03 and Fig. A-FBAAA Sheet

04

NOTE: Ream the holes from the inner side of the fuselage.

To prevent butt strap debonding during reaming, do not remove all

the temporary fasteners at the same time. Install the new fasteners

in the reamed holes one after the other as specified in the steps

that follow.

(k) Countersink the 256 holes in the butt strap Item 7 for the bolts Items 2, 3, 4 and 5.

(l) Deburr the holes.

(m) Attach the butt strap Item 7 and the shim Item 9 with :

Refer to Fig. A-FBAAA Sheet 03, Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet

06

94 Bolt ASNA2026V4-8 Item 2

136 Bolt ASNA2026V4-11 Item 3

26 Bolt ASNA2026V4-13 Item 5

240 Nut ASNA2528-4 Item 1

16 Nut ASNA2531-4 Item 11

NOTE: Apply to the countersunk holes before fastener installation :

Corrosion Inhibiting

Brush Consistency

09-013 As required

(3) Subtask 533127-831-006-001 - Install the butt strap Item 8 and the shim Item 10 at

FR53.3, on the fuselage skin between RH STGR5 and RH STGR13

Work Zones and Access Panels

Zone Access/Work location

250 Work location Frame 53.3

from Stringer 5 RH to Stringer 13 RH

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

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Manpower Resources

Manhours 57.00

Minimum number of person 4

Subtask elapsed time 14.25

Skills AIRFRAME

Material necessary to do the job

Kit 533127A01R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2528-4 240 Nut

2 ASNA2026V4-8 94 Bolt

3 ASNA2026V4-11 136 Bolt

5 ASNA2026V4-13 26 Bolt

8 F5332579120196 1 Strap

10 F5332579220196 2 Shim

11 ASNA2531-4 16 Nut

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013 As required

Sealant 09-016 As required

Chemical Conversion

Coating

13-002 As required

Anti-Corrosion Primer 16-001 As required

Polyurethane Top Coat

Grey

16-002 As required

References

Non Destructive Test Manual (NTM) 51-10-01 Part 6, Procedure A

Fig. A-FBAAA

Butt Strap Installation

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

(a) Remove the fasteners between RH STGR5 and RH STGR13

Refer to Fig. A-FBAAA Sheet 03 and Fig. A-FBAAA Sheet 04

1 Between RH STGR5 and RH STGR13, remove :

Refer to Fig. A-FBAAA Sheet 03

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

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128 Nut Item (1) Discard

56 Bolt Item (2) Discard

72 Bolt Item (3) Discard

Refer to Fig. A-FBAAA Sheet 04

128 Nut Item (1) Discard

38 Bolt Item (2) Discard

64 Bolt Item (3) Discard

26 Bolt Item (5) Discard

(b) Do an inspection of the holes

1 Do a rototest in the 128 holes of the removed bolts, (Refer to NTM 51-10-01

Part 6, Procedure A), (Refer to Fig. A-FBAAA Sheet 03 and Fig. A-FBAAA

Sheet 04).

2 If a crack is found, contact AIRBUS.

3 If no crack is found, do the steps that follow.

(c) Put the butt strap in position on the skin between RH STGR5 and RH STGR13

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 06, Fig. A-FBAAA Sheet 07

and Fig. A-FBAAA Sheet 08

1 As shown in View E, Section BB, Section CC and Section DD, put in position

and hold :

1 Butt Strap F5332579120196 Item 8

1 Shim F5332579220196 Item 10

NOTE (1): Put the shim Item 10 in position between the fuselage skin and

the butt strap Item 8 to fill the clearance between the skin and

the butt strap.

(d) Counter-drill the fastener holes in the butt strap Item 8 and shim Item 10

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 03 and Fig. A-FBAAA Sheet

04

1 In the butt strap Item 8 and the shim Item 10, counter-drill 256 holes,

temporarily attach the butt strap at the same time.

(e) Deburr the holes.

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

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(f) Identify with a mark the upper and lower sides on the butt strap Item 8 before

removal, to prevent a wrong position when you install it.

NOTE: If necessary, adjust the length of the butt strap Item 8 and the

shims Item 10.

Renew the protective finish on the reworked surfaces with :

Chemical

Conversion Coating

13-002 As required

Anti-Corrosion

Primer

16-001 As required

Polyurethane Top

Coat Grey

16-002 As required

(g) Remove the butt strap Item 8 and the shim Item 10.

(h) Apply to the attachment areas between the butt strap, the shim and the fuselage :

Sealant 09-016 As required

(i) Install the butt strap Item 8 and the shim Item 10

Refer to Fig. A-FBAAA Sheet 06, Fig. A-FBAAA Sheet 07 and Fig. A-FBAAA Sheet

08

1 Put the butt strap and the shim in position on the skin, between RH STGR5

and RH STGR13 :

1 Butt Strap F5332579120196 Item 8

1 Shim F5332579220196 Item 10

NOTE: Temporarily attach the parts.

Smooth the burr of sealant.

Let the sealant dry as necessary.

(j) Ream the 256 holes to a diameter between 6.310 mm and 6.350 mm (0.24842 in.

and 0.25000 in.).

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 03 and Fig. A-FBAAA Sheet

04

NOTE: Ream the holes from the inner side of the fuselage.

To prevent butt strap debonding during reaming, do not remove all

the temporary fasteners at the same time. Install the new fasteners

in the reamed holes one after the other as specified in the steps

that follow.

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

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(k) Countersink the 256 holes in the butt strap Item 8 for the bolts Items 2, 3, 4 and 5.

(l) Deburr the holes.

(m) Attach the butt strap Item 8 and the shim Item 10 with :

Refer to Fig. A-FBAAA Sheet 03, Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet

06

94 Bolt ASNA2026V4-8 Item 2

136 Bolt ASNA2026V4-11 Item 3

26 Bolt ASNA2026V4-13 Item 5

240 Nut ASNA2528-4 Item 1

16 Nut ASNA2531-4 Item 11

NOTE: Apply to the countersunk holes before fastener installation :

Corrosion Inhibiting

Brush Consistency

09-013 As required

(4) Subtask 533127-831-007-001 - Apply sealant around the butt straps

Work Zones and Access Panels

Zone Access/Work location

250 Work location Frame 53.3

from Stringer 13 LH to Stringer 13 RH

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant 09-016 As required

(a) Around the butt straps, apply a bed of

Sealant 09-016 As required

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

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SERVICE BULLETIN

(5) Subtask 533127-831-008-001 - Paint the modified area

Work Zones and Access Panels

Zone Access/Work location

250 Work location Frame 53.3

from Stringer 13 LH to Stringer 13 RH

Manpower Resources

Manhours 4.50

Minimum number of person 2

Subtask elapsed time 2.25

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Anti-Corrosion Primer 16-001 As required

External Decoration Paint 16-016 As required

External Top Coat 16-018 As required

(a) Apply

Anti-Corrosion

Primer

16-001 As required

to the bolt heads then apply

External Top Coat 16-018 As required

or

External Decoration

Paint

16-016 As required

to the bolt heads and the butt straps.

D. TEST

(1) Subtask 533127-700-009-001 - Testing

Manpower Resources

Skills NON SPECIFIC

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

REVISION No.: 02 - Dec 07/11 Page: 27

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 05-53-00, Page Block 501

21-20-00, Page Block 401

25-23-41, Page Block 401

25-24-51, Page Block 401

25-24-61, Page Block 401

25-80-00, Page Block 201

(a) Do a test for leakage in the repair area at a differential pressure of 280 mbar (4.06

psi), (Refer to AMM 05-53-00 Page Block 501).

(b) Install the removed equipment

1 Install the electrical wires and the insulation blankets that you disengaged to

get access to the work area, (Refer to AMM 25-80-00 Page Block 201).

NOTE: If you disengaged the support plates of the decoder/encoder

units 200RH17 and 200RH18, put them in position and attach

with the fasteners retained at removal.

2 Install the air distribution ducts that you removed for an easier access to the

work area, (Refer to AMM 21-20-00 Page Block 401).

3 Install the LH and RH lateral overhead stowage compartments at Frame 53.3,

(Refer to AMM 25-24-51 Page Block 401).

4 Install the center stowage compartment at Frame 53.3, (Refer to AMM

25-24-61 Page Block 401).

5 Install the ceiling panels 251PC, 251QC, 252PC and 252QC, (Refer to AMM

25-23-41 Page Block 401).

(c) Do the test after the removal/installation of the ceiling panels, (Refer to AMM

25-23-41 Page Block 401).

(d) Do the test after the removal/installation of the center-overhead stowage

compartments, (Refer to AMM 25-24-61 Page Block 401).

(e) Do the test after the removal/installation of the lateral-overhead stowagecompartments, (Refer to AMM 25-24-51 Page Block 401).

E. CLOSE-UP

(1) Subtask 533127-942-010-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201

52-10-00, Page Block 201

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

REVISION No.: 02 - Dec 07/11 Page: 28

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SERVICE BULLETIN

(a) Put the aircraft on its wheels and remove the jacking equipment, (Refer to

Appendix - 01 ).

(b) Close the passenger/crew door 831, (Refer to AMM 52-10-00 Page Block 201).

(c) Remove the access platform(s).

(d) Disconnect the aircraft electrical ground-connection, (Refer to AMM 12-34-24 Page

Block 201).

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

REVISION No.: 02 - Dec 07/11 Page: 29

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@A330

SERVICE BULLETIN

**CONF ALL

FR38

FR54

STGR5

STGR5

STGR13

STGR13

STGR5

CL

A/C

B C

D

B C

D

A

E

FR53.3

STGR13

STGR5

FR53.3

STGR9 STGR9

A

G_SB_533127_5_BAAA_01_01

Figure A-FBAAA - Sheet 01

Butt Strap Installation

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

REVISION No.: 02 - Dec 07/11 Page: 30

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@A330

SERVICE BULLETIN

**CONF ALL

FR53.3

FWD

SYMBOL REMOVED ITEMS NEW HOLE DIAMETER NEW BOLT NEW NUT

NUT BOLT PN ITEM

ASNA2026V4−8

PN ITEM

(1) (2) 6.310

(0.24842)

6.350

(0.25000) 2 ASNA2528−4 1

(1) 6.310

(0.24842)

6.350

(0.25000) (3) 3 ASNA2528−4 1

FASTENERS NOT REMOVED

CL

A/C

STGR5

STGR4

STGR3

STGR1

STGR2

(1) 6.310

(0.24842)

6.350

(0.25000) ASNA2528−4 1

B

MIN. mm

(in.) (in.)

MAX. mm

DO A ROTOTEST IN THESE HOLES

A

DO A COLD EXPANSION OF THESE HOLES

(REFER TO DETAIL SHEET 5)

(1) 6.350

(0.25000)

LH SIDE SHOWN FROM THE INSIDE

RH SIDE SYMMETRICAL

(5) ASNA2026V4−13 5

ASNA2026V4−11

(3) ASNA2026V4−11 3 ASNA2531−4 11 6.310

(0.24842)

G_SB_533127_5_BAAA_02_00

Figure A-FBAAA - Sheet 02

Butt Strap Installation

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

REVISION No.: 02 - Dec 07/11 Page: 31

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@A330

SERVICE BULLETIN

**CONF ALL

FR53.3

STGR5

STGR6

STGR7

STGR8

STGR9

FWD

SYMBOL REMOVED ITEMS NEW HOLE DIAMETER NEW BOLT NEW NUT

NUT BOLT PN ITEM

ASNA2026V4−8

PN ITEM

(1) (2) 6.310

(0.24842)

6.350

(0.25000) 2 ASNA2528−4 1

(1) 6.310

(0.24842)

6.350

(0.25000) (3) 3 ASNA2528−4 1

FASTENERS NOT REMOVED

C

(in.) (in.)

MIN. mm MAX. mm

DO A ROTOTEST IN THESE HOLES

LH SIDE SHOWN FROM THE INSIDE

RH SIDE SYMMETRICAL

(1) 6.310

(0.24842)

6.350

(0.25000) (3) ASNA2026V4−11 3 ASNA2531−4 11

ASNA2026V4−11

G_SB_533127_5_BAAA_03_00

Figure A-FBAAA - Sheet 03

Butt Strap Installation

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

REVISION No.: 02 - Dec 07/11 Page: 32

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@A330

SERVICE BULLETIN

**CONF ALL

FR53.3

FWD

SYMBOL REMOVED ITEMS NEW HOLE DIAMETER NEW BOLT NEW NUT

NUT BOLT PN ITEM

ASNA2026V4−8

PN ITEM

(1) (2) 6.310

(0.24842)

6.350

(0.25000) 2 ASNA2528−4 1

(1) 6.310

(0.24842)

6.350

(0.25000) (3) 3 ASNA2528−4 1

FASTENERS NOT REMOVED

(1) 6.310

(0.24842)

6.350

(0.25000)

(1) 6.310

(0.24842)

6.350

(0.25000) (5) ASNA2026V4−13 5 ASNA2528−4 1

STGR9

STGR10

STGR11

STGR12

STGR13

MIN. mm

(in.) (in.)

MAX. mm

D

DO A ROTOTEST IN THESE HOLES

(1) 6.350

(0.25000) (3) ASNA2026V4−11 3 ASNA2531−4 11 6.310(0.24842)

LH SIDE SHOWN FROM THE INSIDE

RH SIDE SYMMETRICAL

ASNA2026V4−13

ASNA2026V4−11

(5) 5 ASNA2531−4 11

G_SB_533127_5_BAAA_04_00

Figure A-FBAAA - Sheet 04

Butt Strap Installation

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

REVISION No.: 02 - Dec 07/11 Page: 33

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SERVICE BULLETIN

**CONF ALL

FR53.3

FWD

NUT BOLT

(1)

(1)

=

STGR5

TO A/C CL

A

B

HOLES

N

A

B

MIN. MAX.

REMOVED

ITEMS STDN

MIN. MAX.

NEW

BOLT

NEW

NUT

mm

(in.)

mm

(in.)

(3) 5.75

(0.22638)

5.79

(0.22795) 6.3N 6.227

(0.24516)

6.262

(0.24654) 3

5.75

(0.22638)

5.79

(0.22795) 6.3N 6.227

(0.24516)

6.262

(0.24654)

FASTENERS NOT REMOVED

COLD EXPANSION, HOLES AND FASTENERS DATA

PN/ITEM PN/ITEM

*

START *

HOLE DIAMETER

FINISH *

HOLE DIAMETER

ASNA

2531−4

ASNA

2531−4

11

11

A

− REAM THE START HOLE DIAMETERS WITH THE BUTT STRAP ITEM 6 AND THE SHIMS

ITEM 12 AND 13 ATTACHED TO THE FUSELAGE

− REMOVE THE BUTT STRAP ITEM 6 AND THE SHIMS ITEM 12 AND 13 AND DO THE

COLD EXPANSION OF HOLES IN THE FUSELAGE

LH SIDE SHOWN FROM THE INSIDE

RH SIDE SYMMETRICAL

DETAIL

COLD EXPANSION OF THE HOLES

B

B B A

PRINCIPLE DIAGRAM FOR

THE INSTALLATION

DIRECTION OF THE

EXPANSION SLEEVE:

− ATTACH THE BUTT STRAP ITEM 6 AND THE SHIMS ITEM 12 AND 13 AGAIN TO THE

FUSELAGE AND REAM THE FINISH HOLE DIAMETERS.

(5)

ASNA

2026V4−11

ASNA

2026V4−13 5

G_SB_533127_5_BAAA_05_00

Figure A-FBAAA - Sheet 05

Butt Strap Installation

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

REVISION No.: 02 - Dec 07/11 Page: 34

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SERVICE BULLETIN

**CONF ALL

STGR5

STGR5

STGR13

FR53.3

STGR12

STGR11

A/C CL

STGR13

STGR12

STGR11

10

A

A

9

E

SHIM

6*

* : IF NECESSARY ADJUST THE LENGTH

8*

7*

SHIM

SKIN

PANELS

D

B

B

C

C

D

12 SHIM

SHIM 12

G_SB_533127_5_BAAA_06_00

Figure A-FBAAA - Sheet 06

Butt Strap Installation

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

REVISION No.: 02 - Dec 07/11 Page: 35

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SERVICE BULLETIN

**CONF ALL

FWD

FR53.3

STGR11

STGR12

STGR13

SECTION

7

8

LH

RH

LH

RH

SECTION

7

8

LH

RH

NOTE: LH SIDE SECTIONS SHOWN

RH SIDE SYMMETRICAL

*

9*

10*

LH

RH

9*

10*

: ADJUST IF NECESSARY

B−B

C−C

VIEW LOOKING AFT

G_SB_533127_5_BAAA_07_00

Figure A-FBAAA - Sheet 07

Butt Strap Installation

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

REVISION No.: 02 - Dec 07/11 Page: 36

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SERVICE BULLETIN

**CONF ALL

7

8

LH

RH

6

SECTION

VIEW LOOKING AFT

D−D

12

FR53.3

6

SECTION

A−A

FWD

12*

G_SB_533127_5_BAAA_08_00

Figure A-FBAAA - Sheet 08

Butt Strap Installation

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

REVISION No.: 02 - Dec 07/11 Page: 37

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SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

REVISION No.: 02 - Dec 07/11 Page: 38

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SERVICE BULLETIN

Appendix - 01

**CONF ALL

(1) Jacking procedure for the installation of the butt straps on the fuselage skin at FR53.3, between

STGR13 LH and STGR13 RH

(a) FIXTURE, TOOLS, TEST AND SUPPORT EQUIPMENT

ITEM PART NUMBER QTY DESCRIPTION

RECOMMEND ALTERNATIVE

2 98F07203002000 98F07203002001 6 HOIST TRIPOD

4 98F07203000150 98F07203000120 1 FR17 HOIST

FITTING

5 98F07203000151 98F07203000121 1 FR17 HOIST

FITTING

6 98F07203000140 98F07203000110 1 FR59 HOIST

FITTING

7 98F07203000141 98F07203000111 1 FR59 HOIST

FITTING

8 98F07203000142 98F07203000126 1 FR76 HOIST

FITTING

9 98F07203000143 98F07203000127 1 FR76 HOIST

FITTING

11 343A160KN2 1 LOAD CELL

12 343A1MN3 2 LOAD CELL

13 343A63KN2 3 LOAD CELL

14 343A100KN2 4 LOAD CELL

15 98A07003906200 8 LOAD CELL

ADAPTOR

16 98A07003912200 2 LOAD CELL

ADAPTOR

17 98A07003907200 7 LOAD CELL

ADAPTOR

18 98A07003907201 2 LOAD CELL

ADAPTOR

20 98A07003907202 1 LOAD CELL

ADAPTOR

Refer to Fig. A-FABAA

NOTE: For Main Jack, Front Jack and Safety Jack, use your own standard tool or

refer to SRM 51-51-00.

(b) AIRCRAFT CONFIGURATION

- This jacking procedure is only applicable to the configuration below: The aircraft without :

. Fuel (except undrainable fuel)

. Payload

. Water (potable)

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

REVISION No.: 02 - Dec 07/11 Page: 1

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SERVICE BULLETIN

Appendix - 01

. Baggage containers

. Pallets

. Emergency equipment

. Catering

. Documents and aircraft tool package.

- For the remaining aircraft configuration :

. Refer to Fig. A-FAAAA

NOTE (1): If the aircraft configuration is not the same as the configuration above, contact

AIRBUS.

NOTE (2): If you do other tasks on the aircraft at the same time, contact AIRBUS.

(c) JACKING PROCEDURE

1 Obey the general jacking instructions, (Refer to SRM 51-51-00).

2 Lift the aircraft on the front, main and safety jacks shown in Fig. A-FACAA, (Refer to

AMM 07-11-00, Page Block 201).

3 Install the additional jacking equipment at FR17, FR59 and FR76 (Refer to Fig. AFACAA).

4 Apply the loads to the jacks at FR17, FR59 and FR76, one step after the other

Refer to Fig. A-FACAA

a Gradually apply the loads shown in step 1 to the jacks at FR17, FR59 and FR76.

Wait until the loads on the jacks become stable and make sure that they are within

a tolerance of +/- 10 percent. Make sure that the safety jack at FR87 is in contact

without load.

b Continue the same procedure as above to apply the loads shown in step 2, then

step 3 and step 4.

NOTE: When the loads given in step 4 are stable within a tolerance of

+/- 10 percent on the jacks at FR17, FR59 and FR76, you can

do the procedure given in ACCOMPLISHMENT INSTRUCTIONS,

paragraph B.

(d) CLOSE-UP

1 Gradually decrease the loads one step after the other, from step 4 to zero on the jacks

at FR17, FR59 and FR76 (Refer to Fig. A-FACAA).

2 Remove the jacks at FR17, FR59 and FR76.

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

REVISION No.: 02 - Dec 07/11 Page: 2

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SERVICE BULLETIN

Appendix - 01

3 Lower the aircraft and remove the front, main and safety jacks, (Refer to AMM 07-11-00,

Page Block 201).

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

REVISION No.: 02 - Dec 07/11 Page: 3

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SERVICE BULLETIN

Appendix - 01

**CONF ALL

X

X

X

X

FUSELAGE

AIRCRAFT CONFIGURATION FOR JACKING:

X

X

X

X

X

X

X

X

INSTALLED REMOVED

X

X

X

X

X

INSTALLED REMOVED

NOSE LANDING GEAR

L/H MAIN LANDING GEAR

R/H MAIN LANDING GEAR

LANDING GEARS

MOVABLE ELEMENTS

X

X

X

INSTALLED REMOVED

X

L/H WING

INSTALLED REMOVED

X

X

INSTALLED REMOVED

R/H WING

X

X

INSTALLED REMOVED

ENGINES

L/H ENGINE

R/H ENGINE

PYLONS

L/H PYLON

R/H PYLON

FUEL

O

O

O

EXCEPT UNDRAINABLE FUEL

EQUIPEMENT/FURNISHING INSTALLED REMOVED

X

X

X

X

X

X

X

X

X

X

X

HORIZONTAL STABILIZER

VERTICAL STABILIZER

L/H PAX DOOR 1

R/H PAX DOOR 1

L/H PAX DOOR 2

R/H PAX DOOR 2

L/H PAX DOOR 3

R/H PAX DOOR 3

L/H PAX DOOR 4

R/H PAX DOOR 4

FWD CARGO DOOR

AFT CARGO DOOR

BULK CARGO DOOR

APU

CREW REST X

L/H WINGLET

L/H SLATS

L/H FLAPS

L/H SPOILERS

L/H AILERONS X

X

X

X

X

X

X

X

INSTALLED REMOVED

L/H ENGINE

R/H ENGINE

THRUST REVERSERS

L/H WING TANKS

R/H WING TANKS

TRIM TANKS

FUSELAGE SECTION 11

FUSELAGE SECTION 12

FUSELAGE SECTION 13

FUSELAGE SECTION 14

FUSELAGE SECTION 14A

FUSELAGE SECTION 15

FUSELAGE SECTION 16

FUSELAGE SECTION 17

FUSELAGE SECTION 18

FUSELAGE SECTION 19

FUSELAGE SECTION 19.1

R/H WINGLET

R/H SLATS

R/H FLAPS

R/H SPOILERS

R/H AILERONS

G_SB_533127_5_AAAA_01_01

Figure A-FAAAA - Sheet 01

Aircraft Configuration for Jacking

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

REVISION No.: 02 - Dec 07/11 Page: 4

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SERVICE BULLETIN

Appendix - 01

**CONF ALL

2

5

14

15

17

11

15

20

2

4

14

15

17

12

16

18

12

16

18

2

8

14

15

17

2

9

14

15

17

13

15

17

ITEM

2

DESIGNATION PART NUMBER

6 HOIST TRIPOD

4 1 FR17 HOIST FITTING

5 1 FR17 HOIST FITTING

6 1 FR59 HOIST FITTING

7 1 FR59 HOIST FITTING

8 1 FR76 HOIST FITTING

9 1 FR76 HOIST FITTING

11 1 LOAD CELL

12 2 LOAD CELL

13 LOAD CELL 343A63KN2

14 LOAD CELL 343A100KN2

15 8

16 2

17 7

18 2

20 1

QUANTITY

343A160KN2

LOAD CELL ADAPTOR

LOAD CELL ADAPTOR

LOAD CELL ADAPTOR

LOAD CELL ADAPTOR

LOAD CELL ADAPTOR

2

7

13

15

17

2

6

13

15

17

98F07203002000

98F07203000120

98F07203000121

98F07203000110

98F07203000111

98A07003906200

98A07003912200

98A07003907200

98A07003907202

98A07003907201

98F07203000126

98F07203000127

343A1MN3

3

4

G_SB_533127_5_ABAA_01_01

Figure A-FABAA - Sheet 01

Jacking Equipment

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

REVISION No.: 02 - Dec 07/11 Page: 5

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SERVICE BULLETIN

Appendix - 01

**CONF ALL

JACKING POINTS

MAX.

PERMIS.

LOADS STEP 1 STEP 2 STEP 3 STEP 4

% OF

TOTAL

LOADS

APPLIED LOADS (Kg)

+/− 10%

FR87 (SAFETY JACK)

 (CONTACT ONLY)

FR17 (2 JACKS)

 (SEE NOTE 2)

FR59 (2 JACKS)

 (SEE NOTE 2)

FR76 (2 JACKS)

 (SEE NOTE 2)

4590 0 0 0 00

16820 2800 5610 8410 11210

8050 530 1060 1580 2110 2

15190 3450 6900 10350 13800 12

WITH TWO JACKS, THE LOAD FOR EACH JACK IS THE APPLIED

LOAD DIVIDED BY TWO).

FRONT JACK

LH MAIN JACK

RH MAIN JACK

MAX.

PERMIS.

LOADS

12540

75130

75130

FOR INFORMATION

FOR INFORMATION

FOR INFORMATION

SUPPORT POINTS REMAINING LOADS (Kg)

11200

38100

38100

10

33

33

CORRESPONDING WEIGHT OF THE AIRCRAFT: 114400 (INCLUDING BALLASTS IF ANY)

10

ACTUAL

LOADS

(SEE NOTE 1)

NOTE 2: APPLIED LOADS ARE TOTAL LOADS PER STATION (FOR A STATION

NOTE 1: TO INSTALL KIT A01 (REFER TO ACCOMPLISHEMENT INSTRUCTION,

PARAGRAPH B.), MAKE SURE THAT THE ACTUAL LOADS ARE

IN A TOLERANCE OF +/− 10% OF THE VALUES GIVEN IN STEP 4.

G_SB_533127_5_ACAA_01_01

Figure A-FACAA - Sheet 01

Jacking Procedure

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

REVISION No.: 02 - Dec 07/11 Page: 6

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SERVICE BULLETIN

Appendix - 02

**CONF ALL

Refer to the subsequent Gantt Chart for the detail concerning the elapsed time assumptions.

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

REVISION No.: 02 - Dec 07/11 Page: 1

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SERVICE BULLETIN

Appendix - 02

**CONF ALL

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A330−53−3127

SB ELAPSED TIME

(HOURS)

GET ACCESS

MH ET/S

TOTAL MANHOURS

SB ELAPSED TIME

314.50

56.25

STEPS

66.00 11.00

0 10 15 60

TEST 3.00 1.50

CLOSE−UP 66.00 11.00

MH

ET/S:

PER

MANHOURS

ELAPSED TIME PER STEP

NUMBER OF PERSONS

01

02

THIS CHART IS ONLY A PROPOSAL.

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM.

MANHOURS GIVEN IN VENDOR SERVICE BULLETINS

ARE NOT REFLECTED IN THIS GANTT CHART.

01

02

NOTES:

PER

6

2

6

:

:

INSTALL THE BUTT STRAP AT FR53.3 57.00 14.25 4

57.00 14.25 4

57.00 14.25 4

PAINT THE AREA MODIFIED 4.50 2.25 2

APPLY SEALANT

G_SB_533127_5_ADAA_01_01

BETWEEN LH AND RH STRG5

INSTALL THE BUTT STRAP AT FR53.3

BETWEEN LH STGR5 AND LH STRG13

INSTALL THE BUTT STRAP AT FR53.3

BETWEEN RH STGR5 AND RH STRG13

4.00 2.00 2

5 20 25 30 40 45 50 35 55

Figure A-FADAA - Sheet 01

Gantt Chart

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

REVISION No.: 02 - Dec 07/11 Page: 2

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SERVICE BULLETIN

REPORTING SHEET

TITLE: FUSELAGE - CENTER FUSELAGE - CIRCUMFERENTIAL JOINT FRAME

53.3, STGR 13 LH TO STGR 13 RH - FATIGUE LIFE IMPROVEMENT

MODIFICATION No.: 49403S16334

Please complete the appropriate item (A or B):

A - SB WILL BE embodied YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to

next normal revision or prior to SB embodiment, please indicate required service(s):

Either: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational

documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With

the next feasible revision, this will result in

- Updating of maintenance documentation to show pre and post SB data.

- Updating of maintenance and operational documentation to show post SB data after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically

include them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

REVISION No.: 02 - Dec 07/11 Page: 1

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data

that you provide us will be used to analyse areas of difficulties and to take corrective action to further

improve the quality of our Service Bulletins.

We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

X Reason X List of Materials Operator Supplied X Mod/Inspection

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127

REVISION No.: 02 - Dec 07/11 Page: 1

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.